EP2402722B1 - Einrichtung zur Messung der Geschwindigkeit eines Fluids - Google Patents

Einrichtung zur Messung der Geschwindigkeit eines Fluids Download PDF

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Publication number
EP2402722B1
EP2402722B1 EP11165127.9A EP11165127A EP2402722B1 EP 2402722 B1 EP2402722 B1 EP 2402722B1 EP 11165127 A EP11165127 A EP 11165127A EP 2402722 B1 EP2402722 B1 EP 2402722B1
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EP
European Patent Office
Prior art keywords
profile
probe
aerofoil
section
measuring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Application number
EP11165127.9A
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German (de)
English (en)
French (fr)
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EP2402722A1 (de
Inventor
Christoph Baumgärtner
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Woelke Industrieelektronik GmbH
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Woelke Industrieelektronik GmbH
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
    • G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
    • G01F1/05—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects
    • G01F1/34—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure
    • G01F1/36—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure the pressure or differential pressure being created by the use of flow constriction
    • G01F1/40—Details of construction of the flow constriction devices
    • G01F1/46—Pitot tubes

Definitions

  • the invention relates to a device for measuring the air velocity in suction lines, with a probe which has at least two measuring points for differential pressure measurement, wherein the probe is designed in the manner of a spatial airfoil profile.
  • the fluid to be examined for its velocity is generally a gaseous fluid.
  • the device in question is placed in an associated conduit by means of the probe.
  • This line can be a suction line, as used for example in the context of the ventilation of mines. Of course, this is not mandatory.
  • the probe is designed so that it is equipped with a partially cylindrical and conical cross-section at least two places at which measuring points for differential pressure measurement are available.
  • the Pressure readings determined in this way are converted into electrical signals. From associated mean values of a multiplicity of pressure measured values, conclusions are drawn about the conveying speed.
  • the known device requires a specially designed probe with relatively large dimensions, which must be placed for example in a suction line. This results in a not inconsiderable design effort.
  • the measurement of various gases or vapors in air and consequently the flanking determination of the methane content in the example case can be done independently with a sensor system, as shown in the DE 199 11 867 C2 is used.
  • the known sensor system uses a metal oxide sensor which has a gas-sensitive layer.
  • the gas-sensitive layer can be electrically heated by means of a heater and emits a corresponding sensor signal when exposed to gases or vapors.
  • Prandtl probe which is a fluidic measuring instrument for determining the back pressure.
  • Prandtl tube has an opening in the flow direction for measuring the total pressure and annular at a distance from the tip and the shaft lateral holes for the static pressure measurement. The difference between these two pressures can be measured.
  • the pressure difference in the said Prandtl pipe is not particularly pronounced, so that compromises must be made in terms of measurement accuracy.
  • uncontrolled contamination can occur due to the impact pressure measurement.
  • a position-fixed differential pressure means is provided, which with several Inlet openings and outlet openings is equipped. The previously mentioned problem of any contamination is not addressed.
  • the invention aims to provide a total remedy.
  • the invention is based on the technical problem of further developing such a device for measuring the velocity of a fluid in such a way that the measuring accuracy is increased while at the same time largely eliminating the risk of possible contamination.
  • a generic device for measuring the air velocity in suction lines is provided according to claim 1.
  • a thickness ratio for the airfoil section of particular 0.6 is observed.
  • a specially designed probe is used, namely one which is designed similar to a three-dimensional airfoil profile, that is to say comparable to a section of an airfoil for an aircraft or rotor blade.
  • the procedure is such that one of the two measuring points is arranged on one profile leading edge and the other measuring point is arranged on one or both profile side edges.
  • relatively high velocity differences in the flow around the fluid to be measured are observed in these areas in such airfoils. Large differences in speed correspond to pronounced pressure differences and consequently a high differential pressure.
  • the measurement accuracy compared to previously used facilities can be significantly increased.
  • this design ensures that vortex shedding does not occur de facto in the area of both measuring points. As a result, there are no pronounced pressure fluctuations, so that the total measured differential pressure signal has a quiet time course and thus is particularly suitable for precise measurements.
  • such a spatial airfoil profile can be particularly advantageous and easy to install in a line.
  • the size required for this is low.
  • the guided through the conduit fluid, in particular the gaseous fluid, by the probe is not or practically not affected. This can be attributed to the particularly streamlined profile of the probe.
  • the probe is placed within the conduit or suction conduit so that the flowing fluid first strikes the profile leading edge and the spatial airfoil profile of the probe flows around its two profile side edges after splitting the flow. Because of this predominantly turbulence-free flow around the spatial airfoil profile, it is also to be expected that contaminants will not occur, or practically do not occur, especially in the area of the measuring point. At most, the predominantly straight trailing edge may be used specifically for dirt accumulation, which can be removed easily. In any case, the measuring points are not influenced by particles entrained, for example, in the gaseous fluid.
  • the arrangement of the measuring points on the one hand on the profile leading edge and on the other hand on the profile side edge makes the device according to the invention with respect to the installation conditions insensitive.
  • main benefits are the main benefits.
  • the probe is formed substantially symmetrically in comparison to a central plane of symmetry.
  • "true" wing profiles are regularly not designed symmetrically in order to generate the buoyancy required for flying. For this reason, no profile curvature is observed in the spatial airfoil profile according to the invention.
  • the skeleton line is not curved and the chord and the skeleton line coincide.
  • the interpretation is usually chosen so that the plane of symmetry opposite to which the probe is designed symmetrically in their spatial expression in the nature of the airfoil, passes through the previously discussed chord.
  • the trailing edge is designed predominantly straight.
  • the trailing edge can be used on the one hand as a targeted collecting surface for any deposits, because in this area the pressure is low.
  • the straight trailing edge allows a compact design with low profile depth, which favors the installation in a line. In fact, the low tread depth allows unimpeded installation in, for example, round and appropriately designed openings in the said duct.
  • the respective measuring point is formed as a rule as an inlet opening for the usually gaseous fluid.
  • the respective inlet opening communicates via a measuring channel with a pressure sensor.
  • both measuring channels run predominantly parallel to each other, so that the two pressure sensors for one hand, the measuring point on the profile leading edge and on the other hand, the measuring point on the profile side edge immediately adjacent to each other output side of the measuring channels can be arranged.
  • the two measuring channels can also be fed directly to a suitably designed differential pressure sensor as needed.
  • the measuring point at the profile leading edge of the probe designed in the manner of a spatial airfoil profile is predominantly acted upon by a more or less high dynamic pressure generated by the fluid to be measured and flowing (gaseous).
  • This high back pressure corresponds to a relatively low flow velocity.
  • the flow velocity in the region of the profile side edge or in the region of both profile side edges at the other measuring point is high.
  • a significantly lower pressure than the high front-side dynamic pressure due to the Bernoulli effect is observed here.
  • Both measuring points are found in areas of predominantly laminar and mostly vortex-free flow, so that pressure fluctuations are barely observed.
  • the two measuring points are each designed as a set of measuring points.
  • the measuring points are arranged on the profile side edge in the region of maximum profile thickness of the airfoil. It is also advisable to arrange the inlet openings distributed at the respective measuring point over the length of the spatial airfoil profile. In fact, the individual inlet openings may be placed in a row in the axial direction.
  • the probe is essentially constructed in two parts.
  • the probe is composed of the airfoil section and the terminal section.
  • the airfoil section is formed in the manner of the spatial airfoil profile, whereas the connection section is designed predominantly cylindrical and accommodates only the two measuring channels in its interior.
  • the measuring channels are led to the outside, for example, a line.
  • This line may be the gas suction line.
  • Very particularly preferred is a Gasabsaug ein for ventilation gases for detecting the outflowing gas quantity equipped with the device according to the invention.
  • the outflowing gas may be collected in a mine.
  • the speed of the extracted weather gas or ventilation gas can now be determined in the example case.
  • the available flow cross-section can be drawn from this conclusions on the volumetric gas quantity. This in turn provides information about, for example, the actual amount of extracted methane, if in addition the methane content in the extracted gas is known.
  • the airfoil profile section is generally designed as a connecting piece projecting into the fluid flow to be examined.
  • This nozzle has the trained as a wing profile cross-section. It has proven to be particularly advantageous if the probe or its airfoil profile in cross-section has a thickness reserve of 20% to 40%, preferably 25% to 35% and most preferably one of about 30%.
  • the thickness backing is known to be the distance of the maximum profile thickness of the airfoil from the front edge in relation to the tread depth. One can also speak in this context of the relative thickness reserve.
  • the airfoil profile or the airfoil profile section has in cross section a thickness ratio of about 50% to 70%, in particular about 60% or 0.5 to 0.7, in particular 0.6.
  • the thickness ratio sets the maximum profile thickness of the airfoil profile in relation to the tread depth, ie the distance from the profile leading edge to the profile trailing edge.
  • the selected airfoil profile may be a so-called NACA profile, ie a two-dimensional cross-section of an airfoil profile, which was developed by the National Advisory Committee for Aeronautics (NACA) for the design of wings.
  • a device for measuring the velocity of a fluid which has a special shape of the probe similar to a spatial airfoil profile.
  • the two measuring points for differential pressure measurement can be realized on the one hand on the profile leading edge and on the other hand on a profile side edge or on both profile side edges.
  • both profile side edges are included in the measurement because the probe is a symmetrical spatial structure with a cross section of the airfoil profile. In addition, this can be used to even out any pressure fluctuations or pressure differences between the two profile side edges.
  • a device for measuring the velocity of a fluid 1 is shown.
  • the fluid 1 flows through a conduit 2 in the in Fig. 2 indicated by arrows flow direction.
  • the line 2 is a gas suction line 2, via which ventilation gases or weather gases 1 are fed to a subsequent use.
  • the speed of the fluid 1 in question, in the exemplary embodiment, the speed of the weather gas 1, is now measured with the aid of the device to be described in detail below.
  • the weather gas or ventilation gas 1 is an air mixture in which, for example, methane of specific concentration is present.
  • the device in question has for this purpose a probe 3, the perspective in the Fig. 1 is shown.
  • the probe 3 is designed in two parts in the exemplary embodiment and has an airfoil section 3a and a connection section 3b.
  • the airfoil section 3a dips into the duct 2, whereas the connecting section 3b protrudes from an opening not expressly shown.
  • the probe 3 or whose airfoil section 3a is formed in the manner of a three-dimensional airfoil profile.
  • the probe 3 or its airfoil section 3a has a profile in cross section, which is shown in FIG Fig. 2 an airfoil is approximated or similar.
  • the measuring points 4, 5 are provided on the probe 3.
  • the measuring points 4, 5 are each inlet openings 4, 5 for the fluid 1.
  • the inlet openings 4, 5 communicate with an associated measuring channel 6, 7.
  • the inlet openings 5 are each connected to the measuring channel 6.
  • the inlet openings 4 all communicate with the measuring channel 7 designed separately therefrom.
  • the respective measuring channel 6, 7 is equipped with an only indicated and associated pressure sensor 8, 9.
  • the pressure sensor 8 is assigned to the measuring channel 6, whereas the pressure sensor 9 belongs to the measuring channel 7.
  • a combined (differential) pressure sensor 8, 9 are provided, to which the two measuring channels 6, 7 are connected.
  • the one measuring point 4 is arranged on a profile leading edge 11 of the spatial airfoil profile or of the airfoil profile section 3a.
  • the other measuring point 5 is located on a profile side edge 12 or on both opposite profile side edges 12.
  • the spatial airfoil profile still has a profile trailing edge 13, which is straight in the exemplary embodiment.
  • the two measuring points 4, 5 are each formed as a measuring point crowd 4, 5. Indeed, there are in fact at the profile leading edge 11 a plurality of inlet openings 4, which define the relevant measuring point 4 respectively the measuring point crowd 4. At the respective profile side edge 12 a plurality of inlet openings 5 are also realized, which define the measuring point 5 and the associated measuring point crowd 5.
  • the airfoil profile or the airfoil profile section 3a is equipped at its two opposite side edges 12 with in each case inlet openings 5 or measuring points 5. All measuring points 5 open into the measuring channel 6. This also applies to all measuring points 4, which in contrast communicate with the measuring channel 7.
  • the measuring points 4, 5 or the associated inlet openings 4, 5 are distributed over the length of the airfoil section 3a and arranged in a row.
  • the measuring points or inlet openings 4 on the profile leading edge 11 form both rows in the axial direction or longitudinal direction of the airfoil section 3a and also in its transverse direction.
  • the measuring points 5 at the respective profile side edge 12 each define only one row in the axial direction or longitudinal direction of the airfoil section 3a. In this way, an average pressure is available in the respective measuring channel 6, 7, which is detected by the associated pressure sensor 8, 9.
  • the airfoil profile or the airfoil profile section 3a has a thickness reserve a of approximately 0.3 and 30%, respectively.
  • the thickness backing a or relative thickness backing a denotes the distance of the maximum profile thickness b from the profile leading edge 11.
  • the maximum profile thickness b of the airfoil profile section 3a is indicated by a distance arrow b in the Fig. 2 indicated.
  • the thickness reserve a so the distance of the profile leading edge 11 up to the distance arrow b as identification of the maximum profile thickness in the range of about 0.3 located compared to tread depth I.
  • the tread depth I is the distance between the front edge 11 and the profile Profile trailing edge 13 and is also in the Fig. 2 entered.
  • the maximum profile thickness b is thus found approximately in one third of the way from the profile leading edge 11 to the profile trailing edge 13.
  • the one in the Fig. 2 illustrated airfoil section 3a and the airfoil profile of the probe 3 over a thickness ratio of about 0.6.
  • This thickness ratio sets the maximum profile thickness b in relation to the tread depth I. That is, the ratio b: I is in the embodiment at about 0.6.
  • the ratio b: I is in the embodiment at about 0.6.
  • the pressure is proportional to the square of the flow velocity, pressure differences between the two measuring points 4, 5 can be observed, which are located well above the factor two up to a factor of four.
  • the pressure at the measuring point 4 in the region of the profile leading edge 11 is up to four times as high as at the profiled side edge 12 and the local measuring point 5. This provides a particularly pronounced differential pressure signal at the two associated pressure sensors 8, 9 which allows a particularly accurate measurement of the flow velocity of the fluid 1.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Measuring Volume Flow (AREA)
  • Measuring Fluid Pressure (AREA)
EP11165127.9A 2010-06-10 2011-05-06 Einrichtung zur Messung der Geschwindigkeit eines Fluids Active EP2402722B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201020007801 DE202010007801U1 (de) 2010-06-10 2010-06-10 Einrichtung zur Messung der Geschwindigkeit eines Fluids

Publications (2)

Publication Number Publication Date
EP2402722A1 EP2402722A1 (de) 2012-01-04
EP2402722B1 true EP2402722B1 (de) 2016-06-29

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EP11165127.9A Active EP2402722B1 (de) 2010-06-10 2011-05-06 Einrichtung zur Messung der Geschwindigkeit eines Fluids

Country Status (6)

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EP (1) EP2402722B1 (ru)
CN (1) CN102279283B (ru)
AU (1) AU2011202583B2 (ru)
DE (1) DE202010007801U1 (ru)
EA (1) EA021448B1 (ru)
ZA (1) ZA201104307B (ru)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108225448A (zh) * 2018-03-09 2018-06-29 中国长江电力股份有限公司 一种光纤f-p多参量智能流量传感器及测量方法
CN109900919B (zh) * 2019-03-13 2021-03-23 北京强度环境研究所 一种柱状涡激测速测振传感器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572117A (en) * 1968-05-27 1971-03-23 Eastech Bluff body flowmeter
US3796095A (en) * 1971-10-01 1974-03-12 Eastech Bluff body flowmeter utilizing a movable member responsive to vortex shedding

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3613867A1 (de) * 1986-04-24 1987-10-29 Roland Sommer Vorrichtung und verfahren zur messung der stroemungsgeschwindigkeit einer freien stroemung im raum
DE3765482D1 (de) * 1986-07-23 1990-11-15 Siemens Ag Einrichtung zum messen des massenstromes in einem rohr.
US4768386A (en) * 1986-08-14 1988-09-06 Cambridge Filter Corp. Air pressure measurement element and system incorporating same
CN2349549Y (zh) * 1995-08-04 1999-11-17 王华伸 液体流量检测装置
DE19616100A1 (de) 1996-04-23 1997-10-30 Buehler Ag Verfahren zur Bestimmung des momentanen Massenstroms und der mittleren Korngröße in einer pneumatisch betriebenen Leitung und Vorrichtung zur Durchführung des Verfahrens
CN2287296Y (zh) * 1996-09-02 1998-08-05 吉林市飞特水处理工程有限责任公司 圆形风道风量测量装置
RU2157980C2 (ru) * 1997-01-28 2000-10-20 Центральный аэродинамический институт им. проф. Н.Е. Жуковского Фюзеляжный приемник воздушного давления со стойкой
NO310322B1 (no) * 1999-01-11 2001-06-18 Flowsys As Maling av flerfasestromning i ror
DE19911867C2 (de) 1999-03-17 2002-02-21 T E M Techn Entwicklungen Und Sensorsystem zur Detektion von Gasen und Dämpfen in Luft
US6487918B1 (en) * 2000-12-22 2002-12-03 Mestek, Inc. Airflow sensor for averaging total pressure
ATE440267T1 (de) * 2001-09-19 2009-09-15 Ems Patent Ag Vorrichtung zur messung eines gasverbrauchs
CN2535778Y (zh) * 2001-12-19 2003-02-12 王犇 燃煤锅炉尾部烟气排放烟道的测量标定装置

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572117A (en) * 1968-05-27 1971-03-23 Eastech Bluff body flowmeter
US3796095A (en) * 1971-10-01 1974-03-12 Eastech Bluff body flowmeter utilizing a movable member responsive to vortex shedding

Also Published As

Publication number Publication date
EA021448B1 (ru) 2015-06-30
EP2402722A1 (de) 2012-01-04
CN102279283B (zh) 2015-10-07
ZA201104307B (en) 2012-04-25
AU2011202583B2 (en) 2015-03-12
AU2011202583A1 (en) 2012-01-12
EA201100746A1 (ru) 2011-12-30
CN102279283A (zh) 2011-12-14
DE202010007801U1 (de) 2010-09-02

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